Method of providing wear-resistant coatings, and related articles

ABSTRACT

A method for applying a wear coating on a surface of a substrate is described. A foil of the wear coating is first attached to the substrate surface, and then fused to the surface, e.g., by brazing. The wear coating may be formed from a carbide-type material. The substrate is very often a superalloy material, e.g., a component of a turbine engine. A method for repairing a worn or damaged wear coating applied over a substrate is also described, along with related articles of manufacture.

BACKGROUND OF THE INVENTION

[0001] This invention relates to articles which require wear-resistance,such as components used in turbine engines. In some specificembodiments, it relates to improved techniques for applying suchcoatings to surfaces that are difficult to access.

[0002] Components are used in a wide variety of industrial applications,under a diverse set of operating conditions. In many cases, thecomponents are provided with coatings which impart variouscharacteristics, such as corrosion resistance, heat resistance,oxidation resistance, and wear resistance. As an example, the variouscomponents of turbine engines are often coated with thermal barriercoatings, to effectively increase the temperature at which they canoperate.

[0003] The wear-resistant coatings (often referred to as “wearcoatings”) are frequently used on turbine engine components, such asnozzle wear pads and dovetail interlocks. The coatings provideprotection in areas where components may rub against each other, sincethe rubbing—especially high frequency rubbing—can erode the part.Various coatings may be used for this purpose, e.g., chromium carbide orcobalt-molybdenum-chromium-silicon coatings. The coatings are usuallyapplied by thermal spray techniques, such as air plasma spray (APS),high velocity oxy-fuel (HVOF), and vacuum plasma spray (VPS).

[0004] The thermal spray techniques are quite suitable for applying wearcoatings to many substrates. However, they are sometimes not effectivefor applying the coatings to regions of a substrate which are somewhatinaccessible, since the spray equipment may be too large and cumbersomefor such regions. For example, it can be very difficult to thermallyspray a wear coating on a flange or other surface of a turbine enginepart. Moreover, the spray process, which may include one or more maskingsteps, is sometimes very time-consuming. Thus, new methods forefficiently applying wear coatings to inaccessible regions of asubstrate would be welcome in the art.

SUMMARY OF THE INVENTION

[0005] One embodiment of this invention is a method for applying a wearcoating on a surface of a substrate, comprising the following steps:

[0006] (a) attaching a foil which comprises the wear coating material tothe substrate surface, and then

[0007] (b) fusing the foil to the substrate surface, so that the wearcoating material adheres to the substrate.

[0008] The foil is often prepared by thermally spraying the wear coatingmaterial onto a removable support sheet. Exemplary thermal spraytechniques are high velocity oxy-fuel and air plasma spray. The foil isthen separated from the support sheet, prior to being fused to thesubstrate. The fusing step is usually carried out by brazing. Thesubstrate is very often a superalloy material. This substrate can be acomponent of a turbine engine.

[0009] Examples of wear coating materials are chromium carbide andcobalt-molybdenum-chromium-silicon coatings. The disclosed methodsgreatly enhance the application of wear coatings to areas which areoften inaccessible or difficult to coat by conventional depositiontechniques.

[0010] A method for repairing a worn or damaged wear coating appliedover a substrate is also described. The method comprises the followingsteps:

[0011] (i) removing the worn or damaged wear coating from a selectedarea on the substrate;

[0012] (ii) attaching a foil which comprises the wear coating materialto the substrate surface, covering the selected area; and then

[0013] (iii) fusing the foil to the substrate, so that the wear coatingmaterial adheres to the selected area on the substrate.

[0014] Related articles are also described. They include a substrate,such as a turbine engine component, and a foil of the wear coatingmaterial disposed over the substrate. In preferred embodiments, the foilis fused to the substrate by a braze layer, to provide the wear coatingin the desired location.

[0015] Further details regarding the various features of this inventionare found in the remainder of the specification.

DETAILED DESCRIPTION OF THE INVENTION

[0016] A variety of materials, including but not limited to metals ormetal alloys, can be used as the substrate for the present invention.The term “metal-based” in reference to substrates disclosed hereinrefers to those which are primarily formed of metal or metal alloys, butwhich may also include some non-metallic components, e.g., ceramics,intermetallic phases, or intermediate phases. The substrate can be aheat-resistant alloy, such as a superalloy, which typically has anoperating temperature of up to about 1000-1150° C. The term “superalloy”is usually intended to embrace iron cobalt- or nickel-based alloys,which include one or more other elements such as aluminum, tungsten,molybdenum, titanium, and iron. Superalloys are described in variousreferences, such as U.S. Pat. Nos. 5,399,313 and 4,116,723, bothincorporated herein by reference. High temperature alloys are alsogenerally described in Kirk-Othmer's Encyclopedia of ChemicalTechnology, 3rd Edition, Vol. 12, pp. 417-479 (1980), and Vol. 15, pp.787-800 (1981). Illustrative nickel-base superalloys are designated bythe trade names Inconel®, Nirponic®, Rene® (e.g., Rene® 80-, Rene® 95alloys), and Udimet®. The type of substrate can vary widely, but it isoften in the form of an engine part, such as a turbine nozzle.

[0017] The metal foil is formed from a material suitable for wearresistance. These types of materials are known in the art, and areusually in powder form. Non-limiting examples include chromium carbideor Group 5 a carbides of vanadium, niobium, or tantalum.Cobalt-molybdenum-chromium-silicon wear coatings may also be used. Someof these materials are commercially designated as T800 coatings. Otherwear coating materials are also possible, such as hafnium carbide (HfC),zirconium carbide (ZrC), manganese carbide (MnC), iron carbide (FeC),nickel carbide (NiC), cobalt carbide (CoC), silicon carbide (SiC),tungsten carbide (WC), molybdenum carbide (MoC), titanium carbide (TiC),and boron carbide (BC). Mixtures which contain any of these materialsmay also be employed, e.g., chromium carbide-nickel chromium coatings.Furthermore, cermets made by combining one or more of the carbides withnickel, chromium or cobalt, or with a combination of any of thesemetals, may also be used.

[0018] The wear coating foil can be made by a variety of techniques. Forexample, wear coating powder can be deposited onto a removable supportsheet (usually metallic) as a thin layer of metal, such as about 25microns to about 1300 microns (after surface finishing, (e.g.,grinding), and preferably, from about 100 microns to about 750 micronsin thickness. In some embodiments, the support sheet is actually aremovable substrate, such as a replica or duplicate of the “finalsubstrate” requiring the wear coating. As described below, varioustechniques can be used to subsequently detach the foil from the supportsheet.

[0019] Various thermal spray techniques are usually employed for thedeposition of the wear coating powder onto the support sheet. Examplesinclude vacuum plasma spray (VPS), high velocity oxygen fuel (HVOF), orair plasma spray (APS). Other deposition techniques could be used aswell, such as sputtering, physical vapor deposition (PVD) or electronbeam physical vapor deposition (EBPVD). As one specific illustration,HVOF techniques are known in the art and described, for example, in U.S.Pat. Nos. 5,508,097 and 5,527,591, both incorporated herein byreference. HVOF is a continuous combustion process in which the powderis injected into the jet stream of a spray gun at very high speeds.Those of ordinary skill in the art are familiar with various HVOFdetails, such as the selection of primary gasses, secondary gasses (ifused), and cooling gasses; gas flow rates; power levels; coatingparticle size, and the like.

[0020] As another illustration, plasma spray techniques are also knownin the art and described, for example, in the Kirk-Othmer Encyclopediaof Chemical Technology, 3rd Edition, Vol. 15, page 255, and referencesnoted therein. U.S. Pat. Nos. 5,332,598; 5,047,612; and 4,741,286 arealso instructive in regard to various aspects of plasma spraying, andare incorporated herein by reference. In general, the typical plasmaspray techniques involve the formation of a high-temperature plasma,which produces a thermal plume. The coating material, in the form of apowder, is fed into the plume. The powder particles melt in the plasmaand are accelerated toward the substrate being coated. If the process iscarried out in an air environment, it is often referred to as APS. Thoseof ordinary skill in the plasma spray coating art are familiar withvarious details which are relevant to applying the coating, e.g., plasmaspray parameters such as spray distances (gun-to-substrate); selectionof the number of spray-passes; powder feed rate, torch power, plasma gasselection; and the like.

[0021] Information regarding the other deposition techniques (e.g.,vacuum plasma deposition, sputtering, PVD, and the like) is also readilyavailable. Those of skill in the art will be able to select particularoperating conditions for using each of these techniques to deposit afoil of the wear coating material on the support sheet.

[0022] The support sheet is then removed, leaving the desired metalfoil. Several different techniques can be used to remove the foil fromthe support sheet. For example, if the support sheet is intentionallynot grit-blasted prior to deposition of the coating metal, adhesion ofthe metal to the support sheet will be relatively low, permitting easydetachment of the foil. Alternatively, a release coating can be appliedto the removable support sheet prior to application of the wear coatingmaterial. Suitable release coatings are known in the art. As stillanother alternative, an etchable coating such as aluminum can be appliedto the removable support sheet prior to application of the wear coatingmaterial. After the wear coating material is applied, the coated supportsheet can be treated in a bath of a solution which selectively etchesthe aluminum, such as aqueous potassium hydroxide. Removal of thealuminum layer results in detachment of the foil from the removablesupport sheet.

[0023] In some instances, the substrate surface to which the foil willbe attached is very curved or somewhat irregular. In such a case, it maybe desirable to provide the foil with a substantially identical shape.Relatively thin foils may be somewhat flexible, and can be bent to somedegree to match the curvature of a substrate. Foils of greater thicknessusually are not flexible, but can be shaped by other techniques. Forexample, the removable support sheet discussed above could initially beprovided with the desired curvature of the substrate, prior todeposition of the coating material. If a replica of the final substrateis used as the support sheet, it would already have the desired shapeand curvature.

[0024] Detachment of the removable support sheet results in afreestanding foil of the wear coating material. The foil can then be cutto a size appropriate for the site on the substrate where the coating isdesired, prior to being fused to the substrate. Various techniques canbe used to temporarily hold the foil in place, prior to fusing. Forexample, an adhesive could be used, i.e., one which completelyvolatilizes during the fusing step. Alternatively, the foil could bebolted, clamped, or tack-welded into place.

[0025] The fusing step can be carried out by various techniques. Veryoften, it is a brazing step, and is similar to any conventional brazingoperation. As used herein, “brazing” is generally meant to include anymethod of joining materials that involves the use of a filler material,metal or alloy. One exemplary reference for details regarding brazing isthe text Modem Metalworking, by J. R. Walker, The Goodheart-Willcox Co.,Inc., 1965, pp. 29-1 to 30-24.

[0026] A variety of braze alloy compositions may be used for the presentinvention. Some of them are described in the Kirk-Othmer Encyclopedia ofChemical Technology, 3rd Edition, Vol. 21, pages 342 et seq. If thesubstrate is a nickel-base superalloy, the braze alloy usually containsat least about 40% by weight nickel. (Nickel-containing braze alloys orcobalt-containing braze alloys are usually used with cobalt-basesuperalloys). The braze alloy composition may also contain siliconand/or boron, which serve as melting point suppressants.

[0027] It should be noted that other types of braze alloys may be used,e.g., precious metal compositions containing silver, gold, and/orpalladium, in combination with other metals, such as copper, manganese,nickel, chrome, silicon, and boron. Mixtures which include at least oneof the braze alloy elements are also possible.

[0028] Various techniques for applying the braze alloy can be employed.For example, the braze alloy composition can be applied to the removablesupport sheet, prior to application of the wear coating composition.Various thermal spray techniques can be used to apply the brazecomposition to the removable support sheet, such as HVOF and APS. Othertechniques can also be used, such as sputtering or PVD. When theremovable support sheet is detached, the braze layer will remainattached to the underside of the wear coating layer (i.e., forming abi-layer), for fusing to the final substrate. In those instances inwhich an etchable coating is employed (as discussed above), the brazecomposition would be applied after the etchable coating is deposited.The solution employed to attack the etchable coating should be one whichwill not adversely affect the braze composition or the wear coatingcomposition.

[0029] In an alternative technique for applying the braze alloy, afreestanding braze foil could be employed. Methods for making such brazefoils are known in the art. Moreover, the braze foils are commerciallyavailable from various sources, such as Wesgo and Allied Signal Company.The braze foil can be tack-welded to the substrate, or an adhesive canbe used. The wear coating foil can then be tack-welded or adhesivelyattached to the braze foil. Alternatively, the braze foil can first beattached to the wear coating foil, followed by the attachment of thejoined foils to the substrate.

[0030] As still another alternative, a green braze tape could be used toattach the wear coating foil to the substrate. Such tapes are well knownin the art, and are commercially available, e.g., the Amdry™ line oftapes from Sulzer-METCO, Inc. They can be obtained with an adhesive onone or both sides, so that the tape can be initially attached to eitherthe substrate or the wear coating foil.

[0031] As another alternative, the braze material can be utilized in theform of a slurry, which usually contains metal powder, binder, andoptionally, solvent. A variety of binder materials may be used, e.g.,water-based organic materials such as polyethylene oxide and variousacrylics, or solvent-based binders. Conventional details related to themixing of the slurry are described in various references, such as U.S.Pat. No. 4,325,754, which is incorporated herein by reference. Slurrycompositions are also commercially available. Use of the braze slurrycompositions is advantageous in various situations. For example, whenthe final substrate surface is irregular, or contains pits or crevices,the braze slurry can be used to fill such regions.

[0032] The braze slurry can be applied to the desired region of thefinal substrate, prior to placement of the wear coating foil over thebraze slurry. Various techniques are available for applying the brazeslurry composition. For example, it can be sprayed, painted, ortape-cast onto the final substrate. Alternatively, the braze slurrycomposition can be applied to the surface region of the foil which willcontact the desired region of the substrate. In fact, the braze slurrycomposition could be applied to both the wear coating foil and thesubstrate region which will be in contact with the foil.

[0033] Those of ordinary skill in the art are familiar with otherdetails regarding brazing. Brazing temperatures depend in part on thetype of braze alloy used, and are typically in the range of about 525°C. to about 1650° C. In the case of nickel-based braze alloys, brazetemperatures are usually in the range of about 800° C. to about 1260° C.When possible, brazing is often carried out in a vacuum furnace. Theamount of vacuum will depend in part on the composition of the brazealloy. Usually, the vacuum will be in the range of about 10⁻¹ torr toabout 10⁻⁸ torr.

[0034] If the wear coating is to be applied to an area which does notlend itself to the use of a furnace (e.g., when the component itself istoo large to be inserted into a furnace), a torch or other localizedheating means can be used. For example, a torch with an argon covershield or flux could be directed at the brazing surface. Specific,illustrative types of heating techniques for this purpose include theuse of gas welding torches (e.g., oxy-acetylene, oxy-hydrogen,air-acetylene, air-hydrogen); RF welding; TIG (tungsten inert-gas)welding; electron-beam welding; resistance welding; and the use of IRlamps. As described above, green braze materials usually contain organicbinders which are volatile. Care should be taken when using these typesof heating techniques with the green brazes, to avoid the undesirableeffects of outgassing. For example, the heating step could be carriedout very gradually. Moreover, one could select green tape compositionswhich have low volatile content.

[0035] As mentioned previously, the fusing step can be carried out bytechniques other than brazing. For example, a torch or other heatingtechnique (e.g., the welding techniques mentioned above) can be used forfusing the wear coating foil to the substrate, as an alternative to thevacuum furnace. Regardless of what fusing technique is employed, theresulting wear coating layer is metallurgically bonded to the substrate,and exhibits the properties of wear coatings applied by prior arttechniques.

[0036] The described method can minimize or do away with time-consumingsteps often found in prior art processes. For example, masking stepsthat are usually required when coating selected substrates (or regionsof a substrate) within a component can be eliminated. Instead, thecoating is formed “off-line”, and can be cut to precise dimensions andthen brazed to the selected substrate region. In many instances, thebrazing step can be advantageously carried out during another heatingstep normally carried out in the process. (Braze alloys having meltingtemperatures similar to temperatures used in another heating step couldbe selected).

[0037] When a pre-existing wear coating becomes worn or damaged, it mustbe carefully repaired, to prevent erosion of the underlying substrate.In the case of a turbine engine component, for example, it may benecessary to repair the coating while the turbine is in service, i.e.,after its delivery from the manufacturing site. The process disclosedherein provides a means for rapidly repairing or replacing selectedareas of an existing wear coating, without having to completely removethe coating. The process is especially useful for repairing coatingswhich are situated in areas not easily accessible to other repairtechniques. Thus, the present invention is also directed to a method forrepairing a worn or damaged wear coating applied over a substrate,comprising the following steps:

[0038] (i) removing the worn or damaged wear coating from a selectedarea on the substrate;

[0039] (ii) attaching a foil which comprises the wear coating materialto the substrate surface, covering the selected area; and then

[0040] (iii) fusing the foil to the substrate, so that the wear coatingmaterial adheres to the selected area on the substrate.

[0041] The fusing step in this embodiment is often carried out by usinga torch or other portable heating apparatus. The various wear coatingshave been described previously, e.g., chromium carbide,cobalt-molybdenum-chromium-silicon, and the like.

[0042] Another aspect of this invention is directed to an article whichcomprises a foil of wear coating material fused to a metal-basedsubstrate. The substrate can be formed of various materials, such assuperalloys, and is often in the form of a turbine engine component. Thefoil is usually fused to the substrate by an intervening braze layer, asdescribed above. The braze layer usually has a thickness of about 2.5microns to about 125 microns, and is usually no greater than about 25microns. As those skilled in the art recognize, there may be arelatively small amount of diffusion or migration of the braze layermaterial into the substrate or into the wear coating foil, e.g.,migration into the pores of a wear foil formed by APS. The wear coatingfoil usually has a thickness in the range of about 25 microns to about1300 microns, and preferably, in the range of about 100 microns to about750 microns, after surface finishing. When the foil is fused to thesubstrate, it functions as a wear coating which protects a designatedportion of the substrate, as described previously.

[0043] Some of the preferred embodiments have been set forth in thisdisclosure for the purpose of illustration. However, the foregoingdescription should not be deemed to be a limitation on the scope of theinvention. Accordingly, various modifications, adaptations, andalternatives may occur to one skilled in the art without departing fromthe spirit and scope of the claimed inventive concept.

[0044] All of the patents, articles, and texts mentioned above areincorporated herein by reference.

What is claimed:
 1. A method for applying a wear coating on a surface ofa substrate, comprising the following steps: (a) attaching a foil whichcomprises the wear coating material to the substrate surface, and then(b) fusing the foil to the substrate surface, so that the wear coatingmaterial adheres to the substrate.
 2. The method of claim 1, wherein thefoil is prepared by thermally spraying the wear coating material onto aremovable support sheet to form the foil, followed by separation of thefoil from the removable support sheet.
 3. The method of claim 2, whereinthermal spraying is carried out by a technique selected from the groupconsisting of vacuum plasma deposition, high velocity oxy-fuel, and airplasma spray.
 4. The method of claim 1, wherein the foil is fused to thesubstrate surface by a brazing or welding technique.
 5. The method ofclaim 4, wherein the brazing technique is carried out in a vacuum. 6.The method of claim 4, wherein the brazing technique is carried out byapplying a slurry of the braze composition to a surface of the foil,attaching the foil to the substrate surface so that the brazecomposition is in contact with the substrate surface, and then exposingthe braze composition to a suitable brazing temperature.
 7. The methodof claim 4, wherein the brazing technique is carried out by applying aslurry of the braze composition to the substrate surface; then attachingthe foil to the substrate surface so that the foil is in contact withthe braze composition; and then exposing the braze composition to asuitable brazing temperature.
 8. The method of claim 4, wherein the foilis fused to the substrate surface by a technique which comprises thefollowing steps: (I) applying a layer of braze alloy material to aremovable support sheet; (II) thermally spraying the wear coatingmaterial over the layer of braze alloy material, to form a bi-layer ofbraze alloy and wear coating foil; (III) separating the bi-layer fromthe removable support sheet; (IV) attaching the bi-layer to thesubstrate surface so that braze alloy material is in contact with thesubstrate surface; and then (V) exposing the braze composition to asuitable brazing temperature.
 9. The method of claim 4, wherein thebrazing technique is carried out by attaching the wear coating foil tothe substrate surface with a green braze tape, and then exposing thegreen braze tape to a suitable brazing temperature.
 10. The method ofclaim 1, wherein the wear coating material is selected from the groupconsisting of chromium carbide, vanadium carbide, niobium carbide,tantalum carbide, hafnium carbide, zirconium carbide, manganese carbide,iron carbide, nickel carbide, cobalt carbide, silicon carbide, tungstencarbide, molybdenum carbide, titanium carbide, boron carbide,cobalt-molybdenum-chromium-silicon; and combinations thereof.
 11. Themethod of claim 1, wherein the thickness of the foil is in the range ofabout 25 microns to about 1300 microns.
 12. The method of claim 1,wherein the metal-based substrate is a superalloy.
 13. The method ofclaim 12, wherein the superalloy is nickel-based.
 14. The method ofclaim 1, wherein the substrate is a component of a turbine engine.
 15. Amethod for repairing a worn or damaged wear coating applied over asubstrate, comprising the following steps: (i) removing the worn ordamaged wear coating from a selected area on the substrate; (ii)attaching a foil which comprises the wear coating material to thesubstrate surface, covering the selected area; and then (iii) fusing thefoil to the substrate, so that the wear coating material adheres to theselected area on the substrate.
 16. The method of claim 15, wherein thefusing step is carried out by a brazing technique.
 17. The method ofclaim 16, wherein the brazing technique is carried out by attaching thefoil to the substrate surface with a green braze tape, and then exposingthe green braze tape to a suitable brazing temperature.
 18. The methodof claim 16, wherein the brazing technique is carried out with aportable heating device.
 19. The method of claim 18, wherein theportable heating device is a torch.
 20. The method of claim 15, whereinthe foil is prepared by thermally spraying the wear coating materialonto a removable support sheet to form the foil, followed by separationof the foil from the removable support sheet.
 21. A method for applyinga wear coating on a surface of a superalloy, comprising the followingsteps: (I) preparing a foil of the wear coating material by thermallyspraying a powder of the material onto a removable support sheet to forma foil on the support sheet; (II) separating the foil from the supportsheet; (III) attaching the foil to the superalloy surface; and then (IV)brazing the foil to the superalloy surface so that the wear coatingmaterial adheres to the surface.
 22. The method of claim 21, wherein thewear coating material is selected from the group consisting of chromiumcarbide, tungsten carbide, vanadium carbide, niobium carbide, tantalumcarbide, cobalt-molybdenum-chromium-silicon; and combinations thereof.23. The method of claim 21, wherein the superalloy is a component of aturbine engine.
 24. An article, comprising: (i) substrate; and (ii) afoil which comprises wear coating material fused to the substrate. 25.The article of claim 24, wherein the foil is fused to the substrate byan intervening layer of braze material.
 26. The article of claim 24,wherein the wear coating material is selected from the group consistingof chromium carbide, vanadium carbide, niobium carbide, tantalumcarbide, hafnium carbide, zirconium carbide, manganese carbide, ironcarbide, nickel carbide, cobalt carbide, silicon carbide, tungstencarbide, molybdenum carbide, titanium carbide, boron carbide,cobalt-molybdenum-chromium-silicon; and combinations thereof.
 27. Thearticle of claim 24, wherein the thickness of the foil of wear coatingmaterial is in the range of about 25 microns to about 1300 microns. 28.The article of claim 25, wherein the thickness of the layer of brazematerial is in the range of about 2.5 microns to about 125 microns. 29.An article, comprising: (a) a substrate; (b) a layer of braze materialover the substrate; and (c) a foil of wear coating material over thelayer of braze material, wherein the braze material fuses the substrateto the foil of wear coating material.
 30. The article of claim 29,wherein the substrate is a component of a turbine engine.